Aircraft air conditioner energy recovery method

ABSTRACT

The device involves the placement of an air pump turbine and the aircraft outflow valve in a duct through which all the air flows, with the turbine shaft attached to that of an electric generator, to a hydraulic pump, and to the N2 and accessory gearbox inside the engine, the air is also sent through a duct to strike inclined against the tips of the fan blades and against the tips of the first stage of the low speed compressor blades of the turbine engine.

CROSS-REFERENCES TO RELATED APPLICATIONS

This application is a Continuation in Part of Application Ser. No.09/092,725, filed Jun. 5, 1998, now abandoned, and a continuation ofapplication Ser. No. 09/138,551, filed Aug. 24, 1998, now U.S. Pat. No.6,128,896.

This application claims the priority date of Spanish Patent ApplicationNo. P9800051 filed on Jan. 14, 1998, Spanish Patent Application No.P9800246, filed on Feb. 10, 1996; and Spanish Patent Application No.P9801535, filed on Jul. 20, 1998. The basis for priority in this case isthe Paris Convention for the Protection of Industrial Property (613 O.G.23, 53 Stat 1748). The Spanish patent application was filed in TheOfficial Patent and Trademark Office of Spain.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The field of the invention is aircraft air conditioning exhaust energyrecovery.

2. Description of the Prior Art

At present, aircraft air conditioning exhaust is expelled throughair-flow outlet valves without taking advantage of the potential energycontained in the pressure difference of the interior of the cabin inrelation to the exterior of the aircraft caused by the flow of airrequired for its renewal.

BRIEF DESCRIPTION OF THE INVENTION

The aircraft air conditioning energy recovery device captures thepotential energy held in the pressurized cabin of an airplane flying ataltitude. The pressurized cabin contains potential energy relative tothe unpressurized exterior. As air exits the pressurized cabin,potential energy is converted into kinetic energy as the gas flows out.This kinetic energy can be harnessed and converted to more usable formssuch as electrical energy.

The invention involves the placement of a turbine of an air pump and theaircraft outflow valve in a duct through which the air flows. Theturbine shaft attached to an electric generator, a hydraulic pump, oraccessory gearbox inside the engine, the turbine receives the aircraftair conditioning exhaust from the pressure cabin.

The aircraft air conditioning exhaust can be also sent through a duct tostrike inclined tips of the fan blades and first stage of the low speedcompressor blades of the turbine engine.

In all these cases, the engine efficiency is increased by adding thepotential energy from the pressurized cabin to the system.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows a partial schematic cross-section view of the device of theinvention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

FIG. 1 comprises the air pump turbine (1), the engine (17), the shaft ofthe turbine (9). Air flowing out of the pressurized cabin through duct(18) drives turbine (1) that is connected to a generator (25). Thisgenerator can be any of the following devices: an electric generator, ahydraulic pump, or accessory gearbox (25) via shaft (9), wherein the airoutlet (19) is located. The air is also sent through ducts (21 and 21′),inside the cowl, to strike inclined tips of the fan blades (24), andthrough the duct (22) to strike inclined tips of the blades of the firststage of low speed compressor (23).

What is claimed is:
 1. A method of increasing energy efficiency in anaircraft having a turbine engine with a cowl and said engine having fanblades and an air conditioned cabin with an outlet duct from said cabin,for expelling air conditioned air from said aircraft cabin comprisingthe steps of: channeling said air conditioned air from said aircraftcabin through said outlet duct to said cowl of said engine, distributingsaid air conditioned air from said cabin through one or more ductswithin said engine cowl within said-engine, wherein said air conditionedair strikes inclined tips of said fan blades of said turbine engineadding energy from air conditioned air from said cabin to said engine.2. A method of increasing energy efficiency in an aircraft having aturbine engine with a cowl and said engine having low speed compressorblades and an air conditioned cabin with an outlet duct from said cabin,for expelling air conditioned air from said aircraft cabin comprisingthe steps of: channeling said air conditioned air from said aircraftcabin through said outlet duct to said cowl of said engine, distributingsaid air conditioned air from said cabin through one or more ductswithin said engine cowl within said engine, wherein said air conditionedair strikes said low speed compressor blades of said turbine engineadding energy from air conditioned air from said cabin to said engine.3. A method of increasing energy efficiency in an aircraft having aturbine engine and an air conditioned pressurized cabin with an outletduct from said cabin for expelling air conditioned air from saidaircraft cabin, comprising the steps of: channeling said air conditionedair from said pressurized aircraft cabin to said engine, distributingsaid air conditioned air from said cabin through one or more ductswithin said engine, wherein potential energy of said air conditioned airis converted to kinetic energy as said air exits said pressurized cabinand is harnessed by said engine.